Aeroplane wing construction



April 20, 1937. I D, SUTTON I 2,077,859

. AEROPLANE WING CONSTRUCTION Filed March 30, 1936 INVENTOR.

Patented Apr. 20, 1937 UNITED STATES.

PATENT OFFICE I 2,0TL859 AEROPLANE wmG cons'rnuczrron Donald L. Sutton, Pittsburgh, Pa. Application March so, 1936, Serial No. 71,774 9 Claims; (91. 244-42) The present invention relates to aeroplanes and more particularly to improvements in the wings or sustaining planes therefor. r

The primary object of the invention is to provvide an improved aeroplane wing construction which will provide for increased lateral stability and greater safety in the flying of aeroplanes.

A further object of the invention is to provide an aeroplane wing embodying automatically operable stabilizing means controlled by air pressure or currents acting upon the upper surface of the wing forproviding additional wing balance for the aeroplane.

A further object is to provide in an aeroplane wing construction, means for transferring air from cross wind currents abovethe wing, to the lower side of the wing in the direction of air flow beneath the wing.

A further object is to provide means in an aeroplane wing which will provide for increased lift, and as a stabilizing means for reducing side slipping of the plane.

A still further object is to provide means which may be incorporated in existing wing constructions for increasing the lateral stability or balance of the aeroplane.

Other objects and advantages of the invention will be apparent during the course of the following detailed description, taken in connection with the accompanying drawing forming a part of this specification and in which drawing:

Figure 1 is a top plan view of an aeroplane having the Wing provided with the improvements of this invention and showing the parts in their normal position.

Figure 2 is a view looking at the leading edge of the wing or plane.

Figure 3 is an enlarged vertical sectional view taken transversely thru the wing at one of the 0 stabilizing tubes.

Figure 4 is a section on the line 4-4 of Figure 3.

Figure 5 is an enlarged top plan view of one of the vertical air tubes showing the closure cap closed.

Figure 6 is a section on the line 66 of Figure 5.

Figure '7 is a fragmentary view of theunder side of one end portion of the wing.

Referring to the drawing in detail and wherein similar reference characters designate corresponding parts thruout the several views, the let ,ter A may designate the fuselage of the 55 aeroplane having the sustaining plane or wing Band 4. The closure cap I5 is preferably in the spring hinge I6 is so arranged as to normally hold the closure cap in a vertical position opendesignated as a whole by the letter B, and which extends equally to each side of the fuselage and provides right and left wings 5 and 6 respectively. Provided in each of the wings 5 and 6 is a series of stabilizing devices C and D which are adapted to transfer a portion of the air currents acting upon the upper surface of the wings to the lower side of the wings in the direction of air flow beneath the wings.

Referring first to the stabilizing devices C, the 10 same are of like construction and each embodies a vertical air tube 8 which is preferably of cylindrical formation and provided at its upper end with an outturned rim. 9. These tubes} are adapted to extend thru the wing and have ex- 15 ternallythreaded lower ends for threaded connection with the forward portions of horizontal discharge tubes l0 having an internal diameter equal to that of the air tubes. The discharge tubes l0 are provided adjacent the forward end 20' with a laterally projecting coupling extension II which isinternally screw threaded for receiving the threaded lower end of the tube 8. With this construction, the members 8 and Hi may be readily applied to the wing with the rim '9 engaging 25 the upper surface of the wing and the discharge tube I0 disposed in engagement with the under surface of the wing. The tube I0. is open at its rear end and at" its forward end is closed by a. preferably conical streamlined end for cutting down wind resistance. As will be observed in'Figure 3, the discharge. tube H] extends rearwardly from the vertical air tube 8 whereby the tube In discharges in the direction of air flow beneath the wing. 35

Each of the stabilizing or air transferring devices C is provided'atthe upper end of the vertical air tube 8 with ahinged closure cap l5 normally retained in an open position as shown in Figures 40 form of a thin metal disc suitably connected by a spring hinge IE to the rim 9 whereby the cap may close the upper end of the air tube 8. The

ing the tube 8. The closure cap I5 is provided with suitable perforations H for permitting a.

small amount of air to pass thru the cap and allow for easier opening of the cap against any suction created in the tubes 8 and I0. Suitably mounted at the upper end of the tube 8-are short coil springs l8 which are engaged and compressed by the cap I5 when closed, and these coil springs not only serve to absorb shock when the caps portion l2 0 close upon the rim 8, but also aid in initial opening movement of the cap.

As will be observed, the hinge pins of the spring hinges I8 extend parallel to the discharge tubes ID, or in a direction transversely of the wings and parallel to the fuselage A. It will also be seen from Figures 1 and 2 that the spring hinges l6 are disposed at that side of the air tubes 8 which are nearest to the fuselage A so that the caps I5 of each wing 5 and 8 close in a direction toward the tips of the wings. That is, the position of the closure caps is reversed at opposite sides of the fuselage.

Referring now to the stabilizing devices D, the same are identical in construction to that of the stabilizing devices C with the exception that no closure caps l5 are provided over'the upper ends of their air tubes '8 and air is at all times free to 20 pass from above the wing and be discharged beneath the wing in the direction of air flow, thru the discharge tubes L The devices C and D are preferably made of a suitable metal and will have a diameter and be arranged in suitable numbers and locations upon the wings as will be found desirable for the particular wing to which they are applied. In the example illustrated, the devices have been shown applied to a monoplane having ailerons E. From Figure 1 it will be seen that the devices are arranged in the wings and 8 symmetrically with respect to the fuselage A, with a line or series of the devices D extending transversely of each wing adjacent the fuselage, and a line or series of each of the devices C and D extending transversely of each wing adjacent the tips of the wings. This arrangement and number may vary, however, and likewise the number and arrangement of the devices provided with closure caps'may be varied. As will be observed, the devices are somewhat staggered orstepped and'this is to prevent air currents of one device from interferring with adjacent devices. It willalso be seen that the devices C and D are arranged so as not to interfere 45 with air flow acting upon the ailerons E.

50 venting operation of the closure caps l5. For- While not essential under all flying conditions, the stabilizing devices C and D may be heated if desired to prevent accumulations of snow and ice from partially closing the air passages or prethis purpose, the metal air tubes 8 may be wrapped with a few turns of resistance wire as at r 25 and these turns connected by the conductors 26 to a suitable source of electric current in the 55 fuselage A. Insulating rings 21 may encircle the tubes 8 where they pass thru the wing. This' heating of the tubes 8 will also act to prevent accumulation of snow and ice upon the surfaces of V the wing.

The functioning of the stabilizing devices C and D will be automatic. Supposing the wind to be blowing from the right side of the aeroplane and striking the right wing 5 with greater force than the left wing 6 andtending to force the wing 65 5 down, a considerable amount of this air striking the right wing 5 will pass downwardly thru all of the devices C and D on the wing 5 since the caps l5 of this wing 5 will not be blown shut and thus downward pressure on the wing 5 is reduced. This wind coming from the right will, however, blow the closure caps IS on the left wing Ii down to a closed position over their air tubes and thus increase downward pressure on the wing 75 8 so as to return the aeroplane to an even keel.

Obviously, if the wind blows from the left side of the aeroplane, the action will be reversed and the closure caps l5 on the wing 5 will be closed While those on the wing 6 will remain open. When no cross winds strike the wings, the closure caps I5 all remain in an open vertical position.

Changes in detail may be made to the form of invention herein shown and described without departing from the spirit of the invention or the scope of the following claims.

' I claim( 1. In an aeroplane, a fuselage, a sustaining A plane extending equally to each side of the fuselage, and a plurality of individual air transfer elbows at each side of the fuselage said elbows each having a first conduit extending between the upper and lower surfaces of the plane and a second rearwardly directed conduit below the lower surface of the plane and forming an extension of the first conduit, said second conduit being closed at its forward end and open at its rear end.

2. In an aeroplane, a wing, and stabilizing devices symmetrically arranged at each side of the center of the wing, said devices each including a conduit extending between the upper and lower surfaces of the wing for transferring aircurrents above the wing to the lower side of the wing in the direction of air flow beneath the wing, closure caps for certain of the devices and means urging the caps toward and normally holding the same in an open position, the caps at either end of the wing being arranged to be closed by cross winds approaching from the opposite end of the wing and striking the upper surface of the wing in the direction of its span.

3. In an aeroplane, a wing, a plurality of air tubes extending vertically thru the wing and.

symmetrically arranged at each side of the center of the wing, a discharge tube communicating with the lower end of each air tube and opening rearwardly, hinged closure caps for closing the upper ends of certain of the air tubes and oppositely hinged at opposite sides of the center of the wing, a plurality of springs one urging each cap toward and normally holding the same an open position perpendicular to the wing whereby the caps at either end of the wing may be closed by cross winds approaching from the opposite end of the wing and striking the upper surface of the wing substantially in the direction of its span.

4. In an aeroplane, a fuselage, a wing extending from each side of the fuselage, a plurality ofi discharge tube communicating with the lower.

end-of each air tube, said discharge tubes having a closed forward end and being open at their rear ends, a closure cap hinged to certain of the air tubes of each wing and movable to a closed position toward the tip of their respective wings,

spring means normally retaining the caps open, and spring meanscompressed by the caps when in a closed position.

6. In an aeroplane, a fuselage, a wing extending from each side of the fuselage, a plurality of air tubes extending vertically thru each wing, a discharge tube communicating at its forward end portion with the lower end of each air tube and opening rearwardly, a perforated, spring hinged closure cap for certain of the air tubes of each wing and normally retained in a vertical open position, the caps of each wing being movable to a closed position in a direction toward the tip of the wing, and coil springs for imparting initial opening movement to the caps.

7. In an aeroplane, a wing having air passages therethru and at each side of its'center, closure 15 caps for the upper ends of the air passages, means urging the closure caps toward and normally holding the same in an open upright position, the caps at either side of the wing being hinged to close toward the tip of that side of the wing,

20 whereby the caps at either side of the wing may I close under the influence of cross winds approaching and passing along the upper surface of the wing from the opposite side thereof.

8. In an aeroplane, a fuselage, a wing extending from each side of the fuselage, a plurality of air tubes extending vertically thru each, wing, a rearwardly opening discharge tube communicating with the lower end of each air tube, a hinged cover for certain of the air tubes of each wing and closed toward the tip of the wings,

means normally retaining the caps open, and

means for heating said air tubes.

9. Ina stabilizing unit for aeroplane wings,

comprising an air tube having an outturned rim at its upper end and an externally threaded lower end, a discharge tube of equal diameter as the air tube, having a pointed, closed forward end and being open at its rear end, a laterally projecting,

internally threaded coupling extension at the forward portion of the discharge tube for receiving the lower: forated closure cap for the upper end of the air tube, spring hinge means connecting the closure cap to said rim and normally retaining the cap in an open position, and coil springs mounted in the rim and compressed by; the closure .cap when closed upon the rim.

DONALD L.SUTION-.

end of the air tube, a per- 

